Aeroplane.



L. JONES.

AEROPLANE. APPLICATION FILED FEB. 9| i9l8- 5 SHEETS-SHEET I "If! v Q A? a O '1 Q Q 5- I 51 4mm Patented Dec. 17, I918.

L. JONES.

AEROPLANE.

APPLICATION FILED FEB. 9,1918- 1,287,697. Patented Dec. 17, 1918.

5 SHEETSSHEET 2.

v uvcmtoz L. JONES.

AEROPLANE.

APPLICATION FILED FEB. 9. 1918.

1,287,697, V v Patented Dec. 17, 1918.

-5 YSHEETSSHEET 3.

L. JONES.

\ 'AEROPLANE.

APPLICATION FILED FEB. 9. 1918.

Patented Dec. 17, 1918.

5 SHEETS-SHEET 4.

L. JONES.

AEROPLANE.

APPLICATION FILED FEB. 9. 191a.

ggmg Patented 1m. 1?, I918.

'5. SHEETS-SHEET 5.

LLOYD JONES, 0E LAS ANIMAS, COLORADO.

AEROPLAN E.

Specification of Letters l atent.

Patented Dec. 1'7, 1918.

Application filed February 9, 1918, Serial No. 216,228.

To all whom 2'23 may concern:

' Be it known that I, LLOYD JONES, a citizen of the United States, residing at Las Animas, in the county of Bent and State of Colorado, have invented certain new and use ful Improvements in Aeroplanes, of which the following is a specification.

This invention relates to aeroplanes, and has particular reference to an improved type of aeroplane embodying helicopter principles of construction, wherein is provided an aerial vehicle capable of being sustained and propelled in flight by the action of a rotatable plane structure of novel construction and operation.

Another object of the invention resides in an aeroplane possessing improved features of construction which automatically contribute to maintain the equilibrium of the machine while the latter is in operation, and to insure a controlled and gradual descent thereof in the event of its power plant or other salient member failing to perform its required functional duties.

The invention further comprehends an aeroplane embodying improved features of control and operation, whereby the same will be rendered exceptionally sensitive and responsive to its operators will and guidance.

With these and other objects in View as will appear as the description proceeds, the invention accordingly consists in the novel features of construction, combination of elements and arrangement of parts hereinafter fully described and having the scope thereof defined by the claims hereunto appended.

In the drawing, wherein has been shown a one of the preferred embodiments of the in- 40 vention:

Figure 1 is a vertical sectional view taken through the aeroplane comprising the present invention. I,

Fig. 2 is a top plan view thereof.

' Fig. 3 is a frontelevation.

Fig. 4 is a transverse sectional View taken along the line 4-& of Fig. 1.

Fig. 5 is an enlarged view of the propeller driving mechanism of the aeroplane.

Fig. 6 is a detail sectional view disclosing the manner of mounting the rear rudder,

' Fig. 7 is a detail perspective view of the means for controlling horizontal movements of the rudder,

Fig. 8 is a front elevation of the rudder, the frame of the aeroplane being shown in section,

Fig. 9 is a detail elevation disclosing the means for controlling the vertical oscillating movements of the rudder,

Fig. 10 is a detail transverse sectional view taken through the body of the aeroplane and disclosing more particularly the mechanism for transferring motion from the revolving plane structure to a proper shaft,

Fig. 11 is a detail perspective view of a portion of the rotary wing supporting frame,

Fig. 12 is-a detail sectional view disclosing the means for transmitting motion from the rotary wing frame to the propeller driving sprockets,

ig. 13 is a detail view by canvas if desired. The body further in' cludes a plurality of spaced front and rear end frames 3 and 4 respectively which serve to stabilize and strengthen the general construction of the fuselage.

Suitably mounted within the body 1 is a combustive engine 5 which may be of any standard and approved design, and includes an engine shaft 6, extending fore and aft of the body 1, the ends of the shaft being suitably journaled as shown in Fig. 1. The for ward end of the shaft 6 is provided with a sprocket 7, over which is trained a chain 8, the latter extending to a coiiperative sprocket Scarried by the rear end. .of a for ward propeller shaft 10. The engine shaft is provided with. a manually operated clutch 11, which is adapted to be thrown into engagement with a similar clutch face 12, provided upon the hub of the sprocket 7 disclosing a slightly modified form of the invention,-

of the sprocket By this construction the relative rotation of the shafts 6 and 10 may be readily controlled. v y

The shaft 10 has the forward end thereof journaled in a rojecting frame 13, extending forwardly rom the body 1, and secured to this forward extremity of the shaft 10 is a driving or pulling propeller l i, of common construction and purpose. The frame 13 may be covered with canvas or the like so as to incase the same, and is also pro-' vided with depending alighting wheels 15, forming a running chassis.

The shaft 6 also extends rearwardly and is provided with a sprocket 16, over which a chain 17 is trained, the latter leads to a sprocket 18 carried by a rear propeller shaft 19. The sprocket 18 is loosely mounted upon the latter shaft and may be coupled for rotation therewith through the medium of a clutch 20, which latter is operatively con nected with the means employed for ing the movement of the clutch 11, whereby upon the actuation of a single controlling lever, both clutches may be thrown into driving relation with their cooperative members, and the shafts 10 and 19 will be effected. The rear endof the shaft 19 is provided with a fixed thrust impart-ing propeller 22, which acts in conjunction'with the propeller 14 to effect the propulsion of the aeroplane. By virtue of the clutch construction shown the rotation of said propellers may be conveniently controlled, as will be clearly understood. I

Loosely journaled upon the shaft 19 is a braking propeller 23, and. which has the hub thereof provided with a sprocket 24. Chain 25 is trained over the latter sprocket and leads to a similar sprocket 26 loosely carried upon one end of the engine shaft 6. The hub which is adapted to engage with a slidable clutch element 27 carried by and keyed to the shaft 6. A lever 28 is employed for controlling the movements or positions of the element 27, and therefore, the rotation of the braking propeller 23. The latter is employed for retarding the speed of the aeroplane and is usually set into motion subsequent to the disconnecting of the driving relation existing between the engine shaft 6, and the propeller shafts 10 and 19. It will of course be understood that the propeller 23 may be in a state of rotation simultaneously with the propellers 14 and 22, and in this way will serve to reduce the speed of the aeroplane, but the action of the braking propeller is, of course, rendered more positive and effective by discontinuing the rotation of the driving propellers.

Rigidly carried by the forward end of the frame 13 is a forward elevator plane 29, the latter is usually situated on an angle, with effectwhereby simultaneous rotation of 26 carries a. clutch face,

corresponding respect to the horizontal, so as to be rendered more effective any desirable construction, as the peculiar formation shown does not form an important part of the invention. If desired, the plane 29 may be rendered adjustable, however, such construction is well known in the art and therefore it is not thought necessary to illustrate the same.

Extending rearwardly from the body 1 is a tail frame 30, and which frame also carries a rear elevator plane 31. The latter is structurally similar to the plane 29 and is normally located on substantially the same degree of inclination. This latter plane may be rotatably mounted if desired and through suitable connections, well known to the art, and hence not deemed necessary to illustrate, the said elevator planes may be synchronously oscillated. Frame 30 is also equipped Withan alighting gear 32, carrying traction wheels 33 and whereby, through the provision of similar wheels carried by the gear 15, the machine is rendered portable, and capable of being conveniently set into flight.

The tail frame 30 is of the usual tapering construction, and is preferably covered by canvas or any other suitable part,'so as to conceal its rib construction and to lessen wind resistance. The extreme rear end of the frame 30 terminates in a universal joint 3-l,'to which is connected an aileron or rudder 35, the latter being employed for assisting in controlling the lateral and vertical movements of the aeroplane. The oscillations of the rudder 35 are controlled through the medium of a plurality of cables 36, which are trained over suitable pulleys 37, and have their extremities connected with an operating lever 38. This latter lever is mounted upon a fulcrum, whereby upon moving the lever 38 in specified directions, horizontal movement will be imparted to the rudder 35, as will be clearly understood. A second lever 38' is employed to govern the vertical oscillatory movements of the rudder.

Formed in the circular peripheries of the;

frames 3 and 4 are annular grooves 39, and

in which are rotatably mounted a plurality of diametrically opposed sprockets 40, the latter being fixed upon shafts 4:1, journaled in the frames 3 and 4. Also positioned within the grooves 39 are annular ribs 42, integrally formed upon the circular rotary wing supporting frame 43. Suitable antifriction bearings may be provided between the frames 3 and 4 and the frame 43 so that the rotation of the latter will be attained with but a slight degree of friction. Carried by the frame-4.3 are a plurality of radially disposed rotary balancing planes 44, which latter extend substantially throughout the length of the frame 43 and are formed during the forward travel of the machine. This elevator plane may be of v u h with the usual camber curvature. The surfaces of the planes 44 usually consist of can- .vas stretched over the rib work of the planes. By virtue of this construction it will be seen that the movement of the aeroplane through space results in a whirling rotation of the planes 44, this rotation being positively introduced by reason of the screw like curvature of the planes or wings 44. It is main tained that due to the construction of the planes 44 that the buoyancy 0f the craft is superior to aeroplanes of common construction and that the machine will not be subject to lists or lateral falling. Also, the planes 4 4 permit the machine to ascend or descend with greater rapidity and accuracy than has hitherto been obtainable in aero plane construction and in fact almost true vertical flights may be obtained through skilful operation of the controllers described. In other words, the rotation of the planes 44 has direct bearing upon the altitudinal flights of the machine.

The shafts 41 also carry fixed sprockets 45, which are cooperative with chains 46, leading to similar sprockets 47 carried by sleeves 48, loosely mounted upon the propeller shafts 10 and 19. The sprockets 40 are rotated by meshing with perforated metallic bands 51 carried by the ribs 42. The sleeves 48 are equipped with clutch faces which are adapted to engage with sliding clutch members 49 keyed to said propeller shafts. A manually operated lever 50 is adapted when oscillated to control the operative positions of the members 49. Thus in theevent of the engine becoming disabled, the clutch members 49 may be thrown into engagement with the sleeves 48. This results in effecting the rotation of the propellers 14 and 22 by virtue of the rotation of the planes 44. In this manner the engine may also be rotated for a time so that in case the same has failed by reason of faulty ignition it may be enabled to again begin successful operation by being positively rotated or cranked. If the power plant is permanently disabled the same may be disconnected from the propeller shafts through the clutch mechanisms previously described, whereby the rotation of the planes 44 will be solely-imparted to the propellers 14 and 22 and thus enable the machine operator to effect a desired and controlled landing.

If desired, as shown in Fig. 13, the clutch 49 instead of being manually controlled may 'be of an automatic nature. This is accomplished through the provision of an electroresponsive structure 55, which latter receives its source of energy from a generator 56 driven by the engine 5. The structure 55 normally tends, during the operation of the engine to maintain the clutch 49 out of engagement with the propeller shaft sleeve so that the rotation of the propeller mounted upon said shaft will be independent of the rotation of the planes 44. However, if the engine 5 should become disabled and thereby cease to operate, a spring 57 is provided which tends to force the clutch member 49 into engagement with the sleeves 48, thereby connecting the members 48 and 49 for connected rotation, but normally the force exerted by the structure 55 is sufficient to overcome the tendency of the. spring 57. This construction provides mechanism whereby the wings or planes 4-4 will be automatically connected with the driving propellers in the event of the engine 5 becoming disabled.

From the foregoing it will be seen that there is provided mechanism whereby the objects of the present invention have been achieved and that all of the advantageous features above mentioned are among others present. It will be appreciated, of course, that-I do not limit myself to the precise structure of details shown and described, but that such departure may be made from the present disclosure as will fall within the ambit of the following claims:

That I claim is:

1. An aeroplane comprising a fuselage, a

power plant situated within said fuselage,

driving propellers capable of beingrotated by said power plant, a frame rotatably mounted upon said fuselage, radially ex tending wings carried by said frame, said wings being curved longitudinally to per mit of their rotation during the movement of said aeroplane, and clutch operated means capable of connecting said driving propellers with said wings for synchronous rotation.

2. An aeroplane comprising a fuselage, a power plant located therein, propeller shafts projecting forwardly and rearwardly from said fuselage. driving propellers carried by said shafts, clutch means capable of connecting said power plant with said shafts to effect the rotation of the latter, a retarding propeller loosely mounted upon the rear propeller shaft,- and means for coupling said retarding propeller withsaid power plant.

3. An aeroplane comprising a fuselage, a

power plant situated therein, .propellers located fore and aft of said fuselage and capable of being driven by said power plant,

by said power plant, a frame mounted for rotary movement about said fuselage, radial wings carried by said frame and subject to rotary movement during the progress of the aeroplane, spaced annular rack elements carried by said frame and projecting into annular grooves formed in said fuselage, toothed Wheels journa led for rotation in said grooves and adapted to mesh With said elements, a plurality of sleeves driven by the rotation of said Wheels, and clutch mechanism capable of connecting said sleeves With the shafts of said propellei's, whereby said Wings and propellers may be simultaneously rotated.

LLOYD JONES. 

